Patent GB-740983-A (GB)
Title: Vaporiser and burner for a combustion chamber working with a liquid fuel and a pressurized gaseous oxidizer
Inventor: ALLEN SIDNEY
Filed: 1952-11-20
Abstract: 740,983. Burners. ARMSTRONG SIDDELEY MOTORS, Ltd. Nov. 24, 1953 [Dec. 20, 1952], No. 32354/52. Class 75(1). [Also in Group XII] In combustion equipment, for example, main or exhaust reheat equipment of a gas turbine engine, or a ram jet unit, a casing is disposed within a duct through which combustion-supporting gas such as air flows, the casing being closed at its upstream end and open at its downstream end, fuel being delivered directly on to the external surface of the casing at its upstream end, and fuel and air being induced into the casing at the downstream end. The charge of fuel and air within the casing in burning provides heat for vaporizing the' liquid fuel on the exterior of the casing and also provides a stable flame zone from which the remainder of the vaporised fuel and air are kept burning. The equipment in Figs. 2, 5 and 9 is intended mainly for use`as reheat equipment in the exhaust duct of a gas turbine jet propulsion engine. In Fig. 2, an annular casing 31 is disposed within the jet pipe 24, and fuel is discharged from the manifold 35 on to the inner and outer walls of the casing at the closed end. A mixture of vaporised fuel and exhaust gases is induced into the casing at the downstream end and the mixture is ignited by a pilot flame discharged from the tube 37. The open downstream end of the casing is flared to increase the induction effect. Fig. 5 is similar to Fig. 2 except that fuel is injected into open-ended pockets 49a, 49b mounted on the casing. The casing is supported by means of links 42 from a three-armed spider member 43 which is secured to the exhaust duct, the fuel manifold 35 being similarly supported. In this embodiment, exhaust gas is also introduced into the casing through L-shaped members 52. In Fig. 9 a circular series of can-shaped vaporiser casings 81 is disposed within the duct 24 the casings being inter-connected by pipes 83. Fuel is introduced on to the closed ends of the casings through manifold 35. The apparatus in Figs. 3 and 7 are main combustion apparatus for gas turbine jet propulsion engines. In Fig. 3, which is similar to Fig. 2, the flow into the annular vaporiser casing 31 is supplemented by means of J-shaped pipes 39, the limbs 39b of which receive air and fuel from the manifold 40. In a further embodiment, the J-shaped pipes are disposed almost completely within the annular casing. In Fig. 7 the combustion equipment comprises an annular flame tube disposed in an annular casing 22, 22a and a pair of annular vaporiser casings 31a, 31b is disposed at the inlet of the flame tube, fuel being supplied to the surfaces of the casings from the manifold 35. Additional air and fuel is supplied to the casings through L-shaped pipes 52. The casings are connected by at least one radial tube 54, and for starting a fuel injector and igniter 70 are provided. In the case of a tubular flame tube disposed in a tubular air casing, the vaporiser casing is in the form of a thimble dis. posed at the inlet to the flame tube, fuel being discharged on to the external surface of the closed end of the thimble.